JP2008088976A - Composite turbomachine blade with metal reinforcement - Google Patents

Composite turbomachine blade with metal reinforcement Download PDF

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Publication number
JP2008088976A
JP2008088976A JP2007244800A JP2007244800A JP2008088976A JP 2008088976 A JP2008088976 A JP 2008088976A JP 2007244800 A JP2007244800 A JP 2007244800A JP 2007244800 A JP2007244800 A JP 2007244800A JP 2008088976 A JP2008088976 A JP 2008088976A
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Japan
Prior art keywords
blade
leading edge
recess
aerodynamic surface
reinforcement
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Pending
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JP2007244800A
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Japanese (ja)
Inventor
Stephane Giusti
ステフアン・ジユステイ
Christophe Jacq
クリストフ・ジヤツク
Jean-Pierre Lombard
ジヤン−ピエール・ロンバール
Arnaud Suffis
アルノー・シユフイ
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of JP2008088976A publication Critical patent/JP2008088976A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
    • B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
    • B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
    • B29C65/484—Moisture curing adhesives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/12—Joint cross-sections combining only two joint-segments; Tongue and groove joints; Tenon and mortise joints; Stepped joint cross-sections
    • B29C66/124—Tongue and groove joints
    • B29C66/1246—Tongue and groove joints characterised by the female part, i.e. the part comprising the groove
    • B29C66/12461—Tongue and groove joints characterised by the female part, i.e. the part comprising the groove being rounded, i.e. U-shaped or C-shaped
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/12—Joint cross-sections combining only two joint-segments; Tongue and groove joints; Tenon and mortise joints; Stepped joint cross-sections
    • B29C66/124—Tongue and groove joints
    • B29C66/1246—Tongue and groove joints characterised by the female part, i.e. the part comprising the groove
    • B29C66/12463—Tongue and groove joints characterised by the female part, i.e. the part comprising the groove being tapered
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/301—Three-dimensional joints, i.e. the joined area being substantially non-flat
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
    • B29C66/53—Joining single elements to tubular articles, hollow articles or bars
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/74—Joining plastics material to non-plastics material
    • B29C66/742—Joining plastics material to non-plastics material to metals or their alloys
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
    • B29L2031/082—Blades, e.g. for helicopters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/506—Hardness
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/70—Treatment or modification of materials
    • F05D2300/702—Reinforcement

Abstract

<P>PROBLEM TO BE SOLVED: To provide a composite blade resistant to impact from a foreign body without degrading a set of composite blades to reduce such a fault. <P>SOLUTION: This turbomachine blade comprises an aerodynamic surface made of a composite material and extending in a first direction 14 between a leading edge 16 and a trailing edge 18 and in a second direction between a root and a tip of the blade. The blade includes a solid metal reinforcement 32 adhesively bonded to the leading edge 16 of its aerodynamic surface, and the reinforcement extends along the first direction 14 beyond the leading edge of the aerodynamic surface and along the second direction between the root and the tip, and includes at least one recess 34a for absorbing at least a portion of the energy that results from the impact of the foreign body against the leading edge of the blade. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

本発明は、ターボ機械ブレードの分野に関する。本発明は、より詳細には、複合材料からなり、前縁に金属製の構造補強部が取り付けられるターボ機械のファンブレードに関する。   The present invention relates to the field of turbomachine blades. More particularly, the present invention relates to a turbomachine fan blade made of a composite material and having a metal structural reinforcement attached to a leading edge.

複合材料からなるターボ機械のファンブレードに、ブレードの高さ全体に、また前縁を越えて金属製の構造補強部を取り付けることは知られている。このような補強部は、たとえば鳥がターボ機械に入ってしまった時のように、異物がファンに衝撃を与える際に複合ブレードのセットを保護するために用いられる。   It is known to attach a metal structural reinforcement to a composite turbomachine fan blade over the entire height of the blade and beyond the leading edge. Such a reinforcement is used to protect the set of composite blades when a foreign object impacts the fan, for example when a bird enters the turbomachine.

特に、金属補強部は、ブレードがドレープブレードの場合は層間剥離を回避し、ブレードがウーブンブレードの場合は繊維／マトリクスの分離による損傷または繊維破断による損傷を回避することにより、複合材料からなるブレードの前縁を保護する。   In particular, the metal reinforcement part is a blade made of a composite material by avoiding delamination when the blade is a draped blade and avoiding damage due to fiber / matrix separation or fiber breakage when the blade is a woven blade. Protect the leading edge of the.

ブレードの前縁を覆う金属製の構造補強部があることは、異物による衝撃の場合には複合ブレードのセットを保護するにあたって必ずしも効果的であるとはいえない。   The presence of a metallic structural reinforcement covering the leading edge of the blade is not necessarily effective in protecting the composite blade set in the event of an impact from a foreign object.

従って本発明の主な目的は、複合ブレードのセットを劣化させずに異物からの衝撃に耐え得る複合ブレードを提供することにより、このような短所を軽減することである。   Accordingly, the main object of the present invention is to alleviate such disadvantages by providing a composite blade that can withstand impacts from foreign objects without degrading the set of composite blades.

この目的は、前縁と後縁との間で第１方向に、およびブレード根元部と先端との間で実質的に第１方向に対して垂直の第２方向に沿って延伸する空気力学的表面を備えるターボ機械ブレードにより達成される。上記空気力学的表面は、複合材料からなり、本発明に係りブレードはその空気力学的表面の前縁に接着結合される中実の金属補強部を含み、補強部は第１方向に沿ってブレードの空気力学的表面の前縁を越えて延伸し、第２方向でブレード根元部と先端との間を延伸し、ブレードの前縁に対する異物による衝撃によって生じるエネルギーの少なくとも一部を吸収するための少なくとも１つの凹部を含む。   The purpose is to aerodynamically extend in a first direction between the leading and trailing edges and in a second direction substantially perpendicular to the first direction between the blade root and the tip. This is achieved by a turbomachine blade with a surface. The aerodynamic surface is made of a composite material, and the blade according to the present invention includes a solid metal reinforcement that is adhesively bonded to the leading edge of the aerodynamic surface, the reinforcement being the blade along the first direction. Extending beyond the leading edge of the aerodynamic surface of the blade, extending between the blade root and the tip in the second direction, and absorbing at least a portion of the energy generated by the impact of foreign matter on the leading edge of the blade Including at least one recess.

中実の金属補強部内に少なくとも１つの凹部があることにより、ブレードに対する異物による衝撃によって生じるエネルギーの一部が吸収されることが可能になる。この衝撃エネルギーは、金属補強部の塑性変形により消散する。その結果、ブレード上への異物の衝撃は複合ブレードのセットを著しく劣化させることがなくなる。   By having at least one recess in the solid metal reinforcement, part of the energy generated by the impact of the foreign object on the blade can be absorbed. This impact energy is dissipated by plastic deformation of the metal reinforcing portion. As a result, the impact of foreign matter on the blade does not significantly degrade the composite blade set.

本発明の一実施形態では、凹部は実質的に第１方向へ延伸する。その場合凹部は、ブレードの空気力学的表面の前縁および／または金属補強部の前縁に開口することが可能である。   In one embodiment of the invention, the recess extends substantially in the first direction. In that case, the recess can open to the leading edge of the aerodynamic surface of the blade and / or the leading edge of the metal reinforcement.

別の実施形態では、凹部は実質的に第２方向へ延伸する。その場合凹部は、ブレード根元部の付近および／またはブレードの先端の付近で開口することが可能である。   In another embodiment, the recess extends substantially in the second direction. In that case, the recess can open near the root of the blade and / or near the tip of the blade.

さらに別の実施形態では、凹部は実質的に、第１方向および第２方向に対して垂直の第３方向へ延伸する。その場合凹部はブレードの前面（ｐｒｅｓｓｕｒｅ ｓｉｄｅ）および／またはブレードの後面（ｓｕｃｔｉｏｎ ｓｉｄｅ）に開口することが可能である。   In yet another embodiment, the recess extends substantially in a third direction perpendicular to the first direction and the second direction. In that case, the recesses can open to the front side of the blade and / or to the back side of the blade.

中実の金属補強部は、チタンをベースに製造されることが可能である。ブレードはターボ機械のファンブレードを構成することが可能である。   The solid metal reinforcement can be manufactured based on titanium. The blade may constitute a fan blade of a turbomachine.

本発明は、上述のブレードを少なくとも１つ含むターボ機械も提供する。   The invention also provides a turbomachine comprising at least one blade as described above.

本発明のその他の特徴および利点は、添付の図面と関連する以下の説明から明らかになる。本発明は図面に示される実施形態に限定されるものではない。   Other features and advantages of the present invention will become apparent from the following description taken in conjunction with the accompanying drawings. The present invention is not limited to the embodiments shown in the drawings.

図１から図３は、本発明の実施形態をなすターボ機械のブレード１０を示す。一例として、ブレードはターボ機械ファンの可動ブレードである。   1 to 3 show a turbomachine blade 10 according to an embodiment of the present invention. As an example, the blade is a moving blade of a turbomachine fan.

ブレードは、前縁１６と後縁１８との間で軸方向の第１方向１４に、および第１方向１４に対して実質的に垂直である径方向の第２方向２０に根元部２２と先端２４との間で延伸する。ブレードの一部の断面を示す図２に示されるように、ブレードは、前面２８と後面３０との間で第１および第２方向に対して垂直である接線方向の第３方向２６へも延伸する空気力学的表面１２を呈する。ブレードの前面および後面は、ブレードの前縁１６と後縁１８とを相互に接続する側面を形成する。   The blade has a root 22 and a tip in a first axial direction 14 between the leading edge 16 and the trailing edge 18 and in a second radial direction 20 that is substantially perpendicular to the first direction 14. 24. As shown in FIG. 2, which shows a cross-section of a portion of the blade, the blade also extends between a front surface 28 and a rear surface 30 in a third tangential direction 26 that is perpendicular to the first and second directions. Presenting an aerodynamic surface 12. The front and rear surfaces of the blade form side surfaces that interconnect the leading edge 16 and trailing edge 18 of the blade.

ブレード、より詳細にはその空気力学的表面１２は、上述のように、複合材料のドレーピングまたはウィービングにより得られる。たとえば複合材料は、樹脂トランスファー成形（ＲＴＭ）として知られている真空注入法により織られ成形された炭素繊維のアセンブリであることが可能である。   The blade, and more particularly its aerodynamic surface 12, is obtained by draping or weaving of the composite material as described above. For example, the composite material can be an assembly of carbon fibers woven and shaped by a vacuum injection process known as resin transfer molding (RTM).

本発明のブレードの空気力学的表面１２は金属製の構造補強部３２を含み、これは、その前縁１６に接着結合され、ブレードの空気力学的表面の前縁１６を越えて第１方向１４に、およびブレード根元部２２と先端２４との間で第２方向２０へ延伸する。   The aerodynamic surface 12 of the blade of the present invention includes a metallic structural reinforcement 32 that is adhesively bonded to its leading edge 16 and extends beyond the leading edge 16 of the blade's aerodynamic surface in a first direction 14. And in the second direction 20 between the blade root 22 and the tip 24.

図２および図３に示されるように、構造補強部３２は、空気力学的表面の前縁１６の形状に正確に合わせられ、前縁１６’を形成するよう延伸する。これは本明細書では補強部の前縁とする。たとえば、前縁１６と後縁１８との間の距離が５０ｃｍであるブレードでは、前縁１６と１６’との間の距離は第１方向１４でおよそ３から４センチメートル（ｃｍ）である（すなわち上記距離の６から８％である）。   As shown in FIGS. 2 and 3, the structural reinforcement 32 is precisely matched to the shape of the leading edge 16 of the aerodynamic surface and extends to form the leading edge 16 '. This is the front edge of the reinforcing portion in this specification. For example, in a blade where the distance between the leading edge 16 and the trailing edge 18 is 50 cm, the distance between the leading edges 16 and 16 'is approximately 3 to 4 centimeters (cm) in the first direction 14 ( Ie 6 to 8% of the distance).

さらに、構造補強部３２は、第１方向１４で空気力学的表面の前縁１６を越えて延伸し、ブレードの前面２８および後面３０の輪郭に正確に合わされている。   In addition, the structural reinforcement 32 extends beyond the leading edge 16 of the aerodynamic surface in the first direction 14 and is precisely aligned with the contours of the front and rear surfaces 28 and 30 of the blade.

本発明の構造補強部３２は中実（一体構造）であり、つまり補強部は横断面および長手方向断面いずれにおいても材料が満たされている。たとえば、図２に示されるように、断面において前縁１６と１６’との間で途切れている部分がない。   The structural reinforcing portion 32 of the present invention is solid (integrated structure), that is, the reinforcing portion is filled with a material in both a transverse section and a longitudinal section. For example, as shown in FIG. 2, there is no break in the cross section between the leading edges 16 and 16 '.

ブレードの構造補強部３２は金属製であり、好ましくはチタンベースである。この材料は、衝撃によるエネルギー吸収能力が高い。補強部はブレードに接着結合されており、接着剤はシアノアクリレートまたはエポキシ接着剤を使用することが可能である。   The structural reinforcement 32 of the blade is made of metal and is preferably a titanium base. This material has a high energy absorption capability by impact. The reinforcement is adhesively bonded to the blade, and cyanoacrylate or epoxy adhesive can be used as the adhesive.

さらに、本発明に係り、ブレードの金属補強部３２は、ブレードの前縁に対する異物の衝撃によって生じるエネルギーの少なくとも一部を吸収するための少なくとも１つの凹部を含む。   Further in accordance with the present invention, the metal reinforcement 32 of the blade includes at least one recess for absorbing at least a portion of the energy generated by the impact of a foreign object against the leading edge of the blade.

ブレードの金属補強部内の凹部の数、形状、位置および方向は、用途に応じて異なることが可能である。これらのパラメータは、起こり得る最も危機的な衝撃に応じて決定および最適化される。   The number, shape, position and direction of the recesses in the metal reinforcement of the blade can vary depending on the application. These parameters are determined and optimized according to the most critical impact that can occur.

本発明のブレードの金属補強部の凹部の様々な好ましい形状について以下に説明する。   Various preferable shapes of the concave portion of the metal reinforcing portion of the blade of the present invention will be described below.

図３、図４Ａおよび図４Ｂの実施形態では、補強部３２は、ブレードの第１方向１４に沿って延伸する中空キャビティ３４ａの形を有する。   In the embodiment of FIGS. 3, 4A and 4B, the reinforcement 32 has the form of a hollow cavity 34a extending along the first direction 14 of the blade.

より詳細には、図３に示される変形例では、凹部は、ブレードの空気力学表面１２の前縁１６で開口する中空キャビティ３４ａである。   More particularly, in the variant shown in FIG. 3, the recess is a hollow cavity 34a that opens at the leading edge 16 of the aerodynamic surface 12 of the blade.

図４Ａの変形例では、凹部は、金属補強部３２の前縁１６’へ開口する中空キャビティ３４ａである。   In the modification of FIG. 4A, the recess is a hollow cavity 34 a that opens to the front edge 16 ′ of the metal reinforcement portion 32.

図４Ｂの凹部３４ａは、空気力学的表面１２の前縁１６および金属補強部３２の前縁１６’への両方に開口する。   The recess 34a of FIG. 4B opens both to the leading edge 16 of the aerodynamic surface 12 and to the leading edge 16 'of the metal reinforcement 32.

図５Ａおよび図５Ｂの実施形態では、補強部３２における凹部は、ブレードの第２方向２０に延伸する中空キャビティ３４ｂの形を有する。   In the embodiment of FIGS. 5A and 5B, the recess in the reinforcement 32 has the form of a hollow cavity 34b extending in the second direction 20 of the blade.

この中空キャビティ３４ｂは、ブレード根元部２２および／または先端２４の付近で開口することが可能である。ブレード根元部の付近および先端の付近両方で開口する中空キャビティでは、ブレードに空気流が通り得、これはターボ機械の空力性能の向上に寄与する。   The hollow cavity 34 b can open near the blade root 22 and / or the tip 24. In hollow cavities that open both near the blade root and near the tip, air flow can pass through the blade, which contributes to improved aerodynamic performance of the turbomachine.

さらに、図５Ａに示されるように、金属補強部内の凹部は、実質的に円形の断面の単一の中空キャビティ３４ｂにより形成されることも可能である。または、図５Ｂに示されるように、凹部は複数のキャビティ（図示される実施例では３つ）からなることも可能である。   Further, as shown in FIG. 5A, the recess in the metal reinforcement may be formed by a single hollow cavity 34b having a substantially circular cross section. Alternatively, as shown in FIG. 5B, the recess may consist of a plurality of cavities (three in the illustrated embodiment).

当然、その他の断面形状も可能である（楕円、多角形等）。さらに、キャビティの寸法は、ブレードの全体の高さに渡って異なることが可能であり、これによりブレードに衝突する異物の質量およびブレードの高さを含む組み合わせに適合されることが可能である。   Of course, other cross-sectional shapes are possible (elliptical, polygonal, etc.). Furthermore, the dimensions of the cavity can vary over the entire height of the blade, which can be adapted to combinations including the mass of foreign matter impinging on the blade and the height of the blade.

図６Ａおよび図６Ｂの実施形態では、補強部３２の凹部は、ブレードの第３方向２６に沿って延伸する中空キャビティ３４ｃの形を有する。   In the embodiment of FIGS. 6A and 6B, the recess of the reinforcement 32 has the shape of a hollow cavity 34c extending along the third direction 26 of the blade.

より詳細には、図６Ａの変形例では、２つの凹部が設けられ、これらはいずれもブレードの前面２８およびブレードの後面３０へ開口する中空キャビティ３４ｃを有する。従って、凹部は前面と後面との間の空気流を伝える役割を有し、これによりターボ機械の空力性能の向上に寄与する。   More specifically, in the variation of FIG. 6A, two recesses are provided, both having a hollow cavity 34c that opens to the blade front surface 28 and the blade rear surface 30. Therefore, the concave portion has a role of transmitting an air flow between the front surface and the rear surface, thereby contributing to improvement of the aerodynamic performance of the turbomachine.

図６Ｂに示される変形例では、２つの凹部が設けられ、いずれもブレードの後面３０のみに開口する中空キャビティ３４ｃから構成される。   In the modification shown in FIG. 6B, two concave portions are provided, and each is constituted by a hollow cavity 34 c that opens only on the rear surface 30 of the blade.

図３、図４Ａ、図４Ｂ、図５Ａ、図５Ｂ、図６Ａおよび図６Ｂの実施形態では、凹部は中空のキャビティ３４ａから３４ｃとして実現されている。しかし、これらのキャビティを非構造材料（すなわち中実を有さない材料）で満たし、輪郭の表面を再現することも考えられる。たとえば非構造材料は、ポリマー、ゴムまたはシリコーンであることが可能である。   In the embodiments of FIGS. 3, 4A, 4B, 5A, 5B, 6A and 6B, the recesses are realized as hollow cavities 34a to 34c. However, it is also conceivable to fill these cavities with non-structural materials (i.e. materials without solids) and to reproduce the contoured surface. For example, the non-structural material can be a polymer, rubber or silicone.

本発明のブレードの長手方向断面図である。It is longitudinal direction sectional drawing of the braid | blade of this invention. 図１のＩＩ−ＩＩにおける部分断面図である。It is a fragmentary sectional view in II-II of Drawing 1. 図１のＩＩ−ＩＩおよびＩＩＩ−ＩＩＩにおける部分断面図である。It is the fragmentary sectional view in II-II and III-III of FIG. 図１のブレードの変形例を示す部分断面図である。It is a fragmentary sectional view which shows the modification of the braid | blade of FIG. 図１のブレードの変形例を示す部分断面図である。It is a fragmentary sectional view which shows the modification of the braid | blade of FIG. 本発明の別の実施形態のブレードを示す部分断面図である。It is a fragmentary sectional view showing a blade of another embodiment of the present invention. 本発明の別の実施形態のブレードを示す部分断面図である。It is a fragmentary sectional view showing a blade of another embodiment of the present invention. 本発明のさらに別の実施形態のブレードを示す部分断面図である。It is a fragmentary sectional view showing a blade of another embodiment of the present invention. 本発明のさらに別の実施形態のブレードを示す部分断面図である。It is a fragmentary sectional view showing a blade of another embodiment of the present invention.

符号の説明Explanation of symbols

１０ ブレード
１２ 空気力学的表面
１４ 第１方向
１６ 前縁
１８ 後縁
２０ 第２方向
２２ 根元部
２４ 先端
２６ 第３方向
２８ 前面
３０ 後面
３２ 補強部
３４ａ、３４ｂ、３４ｃ 中空キャビティ DESCRIPTION OF SYMBOLS 10 Blade 12 Aerodynamic surface 14 1st direction 16 Leading edge 18 Trailing edge 20 2nd direction 22 Root part 24 Tip 26 3rd direction 28 Front surface 30 Rear surface 32 Reinforcement part 34a, 34b, 34c Hollow cavity

Claims (10)

前縁（１６）と後縁（１８）との間で第１方向（１４）に沿って、およびブレード根元部（２２）と先端（２４）との間で第１方向に対して実質的に垂直である第２方向（２０）に沿って延伸する空気力学的表面（１２）を備えるターボ機械ブレード（１０）において、前記空気力学的表面は複合材料からなり、空気力学的表面の前縁（１６）に接着結合される中実の金属補強部（３２）を含み、補強部が第１方向（１４）に沿ってブレードの空気力学的表面の前縁を越えて延伸し、ブレード根元部と先端との間で第２方向（２０）へ延伸し、ブレードの前縁に対する異物の衝撃によって生じるエネルギーの少なくとも一部を吸収するための少なくとも１つの凹部（３４ａ、３４ｂ、３４ｃ）を含むことを特徴とする、ブレード。   Substantially along the first direction (14) between the leading edge (16) and the trailing edge (18) and between the blade root (22) and the tip (24) relative to the first direction. In a turbomachine blade (10) comprising an aerodynamic surface (12) extending along a second direction (20) that is perpendicular, said aerodynamic surface is made of a composite material and the leading edge of the aerodynamic surface ( 16) a solid metal reinforcement (32) adhesively bonded to the blade, the reinforcement extending along the first direction (14) beyond the leading edge of the aerodynamic surface of the blade, Extending in the second direction (20) between the tip and including at least one recess (34a, 34b, 34c) for absorbing at least a portion of the energy generated by the impact of a foreign object on the leading edge of the blade. Features a blade. 凹部（３４ａ）が実質的に第１方向（１４）に沿って延伸する、請求項１に記載のブレード。   The blade according to claim 1, wherein the recess (34a) extends substantially along the first direction (14). 凹部（３４ａ）が、ブレードの空気力学的表面（１２）の前縁（１６）および／または中実の金属補強部（３２）の前縁（１６’）に開口する、請求項２に記載のブレード。   The recess (34a) according to claim 2, wherein the recess (34a) opens in the leading edge (16) of the aerodynamic surface (12) of the blade and / or the leading edge (16 ') of the solid metal reinforcement (32). blade. 凹部（３４ｂ）が実質的に第２方向（２０）に沿って延伸する、請求項１に記載のブレード。   The blade according to claim 1, wherein the recess (34b) extends substantially along the second direction (20). 凹部（３４ｂ）が、ブレード根元部（２２）の付近および／またはブレードの先端（２４）の付近に開口する、請求項４に記載のブレード。   The blade according to claim 4, wherein the recess (34b) opens near the blade root (22) and / or near the blade tip (24). 凹部（３４ｃ）が、第１方向（１４）および第２方向（２０）に対して実質的に垂直である第３方向（２６）に沿って延伸する、請求項１に記載のブレード。   The blade according to claim 1, wherein the recess (34c) extends along a third direction (26) that is substantially perpendicular to the first direction (14) and the second direction (20). 凹部（３４ｃ）が、ブレードの前面（２８）および／またはブレードの後面（３０）に開口する、請求項６に記載のブレード。   The blade according to claim 6, wherein the recess (34c) opens in the front surface (28) of the blade and / or the rear surface (30) of the blade. 中実の金属補強部（３２）がチタンをベースに製造される、請求項１から７のいずれか一項に記載のブレード。   The blade according to any one of the preceding claims, wherein the solid metal reinforcement (32) is manufactured on a titanium base. ターボ機械のファンのブレードを構成する、請求項１から８のいずれか一項に記載のブレード。   The blade according to claim 1, which constitutes a blade of a turbomachine fan. 請求項１から９のいずれか一項に記載の少なくとも１つのブレード（１０）を含む、ターボ機械。   A turbomachine comprising at least one blade (10) according to any one of the preceding claims.
JP2007244800A 2006-09-26 2007-09-21 Composite turbomachine blade with metal reinforcement Pending JP2008088976A (en)

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